Fast prediction method for rotor blade tip deformation through a fusion of analytical and numerical models and its application

Facing the rapid and precise design requirements for engine clearance， a fast prediction method for rotor blade tip deformation is presented through a fusion of analytical and numerical approaches. The method integrates rapid analytical calculations for the deformation of complex swept blades， automatic numerical solutions for intricate disk configurations， and corrections for blade-disk attachments. This enables high-speed and accurate calculations of blade tip deformation under the combined effects of centrifugal forces， temperature， and their interactions. The proposed method is applied to predict the blade tip deformation of actual engine compressors and turbines， and compared with solid finite element approaches and purely analytical approaches found in literature. The results demonstrate that the predicted blade tip deformation values from this method exhibit less than 2% error compared to finite element results， while showing significantly greater accuracy than existing purely analytical approaches. Additionally， the proposed method is at least two orders of magnitude more efficient than solid finite element approaches. By establishing an automated solution process and a software using MATLAB and ANSYS， this method achieves solution times comparable to purely analytical methods. This research offers an efficient and precise computational strategy for rotor blade tip deformation， effectively supporting clearance evaluation and iterative optimization during engine design stages.